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<title> DU 91-W2-250 </title></head>

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<H1>DU 91-W2-250 AIRFOIL</H1>
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Reynolds number = 1.0 x 10^6 <br><br>

Measured in the low-speed low-turbulence wind tunnel of the Faculty
of Aerospace Engineering of Delf University (see <A
HREF="./../HTML/biblio.htm#Timmer">Timmer</A>) <br><br>

More details on computations and experimental facilities can be found in
the <A HREF="./../HTML/report.htm"><font color="#006699">Wind Turbine
Airfoil Catalogue</font></A>.


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<H1>DATA AVAILABLE:</H1><p><p>

- <A HREF="./prof.dat"> Airfoil shape </A><p>

<font size=+3> Experiments:<br> </font>
- <A HREF="./cldm.exp"> Lift, Drag and Moment Coefficients </A><p>

- <A HREF="./cp_07.686.exp"> Pressure Distribution - Angle of Attack = 07.686 deg. </A><br>
- <A HREF="./cp_09.742.exp"> Pressure Distribution - Angle of Attack = 09.742 deg. </A><br>
- <A HREF="./cp_11.712.exp"> Pressure Distribution - Angle of Attack = 11.712 deg. </A><br>
- <A HREF="./cp_15.190.exp"> Pressure Distribution - Angle of Attack = 15.190 deg. </A><p>

<font size=+3> XFOIL Computations:<br> </font>
- <A HREF="./cldm.xf"> Lift, Drag and Moment Coefficients </A><p>
- <A HREF="./cfp_07.686.xf"> Skin Friction and Pressure Distributions - Angle of Attack = 07.686 deg. </A><br>
- <A HREF="./cfp_09.742.xf"> Skin Friction and Pressure Distributions - Angle of Attack = 09.742 deg. </A><br>
- <A HREF="./cfp_11.712.xf"> Skin Friction and Pressure Distributions - Angle of Attack = 11.712 deg. </A><br>
- <A HREF="./cfp_14.000.xf"> Skin Friction and Pressure Distributions - Angle of Attack = 14.000 deg. </A><br>
- <A HREF="./cfp_15.190.xf"> Skin Friction and Pressure Distributions - Angle of Attack = 15.190 deg. </A><br>
- <A HREF="./cfp_16.000.xf"> Skin Friction and Pressure Distributions - Angle of Attack = 16.000 deg. </A><p>

<font size=+3> EllipSys2D Computations: </font><p>
<font size=+2><em>* With transition model:</em><br> </font>
- <A HREF="./cldm.ellipsys"> Lift, Drag and Moment Coefficients </A><p>
- <A HREF="./cp_07.686.ellipsys"> Pressure Distribution - Angle of Attack = 07.686 deg. </A><br>
- <A HREF="./cp_09.742.ellipsys"> Pressure Distribution - Angle of Attack = 09.742 deg. </A><br>
- <A HREF="./cp_11.712.ellipsys"> Pressure Distribution - Angle of Attack = 11.712 deg. </A><br>
- <A HREF="./cp_14.000.ellipsys"> Pressure Distribution - Angle of Attack = 14.000 deg. </A><br>
- <A HREF="./cp_15.190.ellipsys"> Pressure Distribution - Angle of Attack = 15.190 deg. </A><br>
- <A HREF="./cp_16.000.ellipsys"> Pressure Distribution - Angle of Attack = 16.000 deg. </A><p>

- <A HREF="./cf_07.686.ellipsys"> Skin Friction Distribution - Angle of Attack = 07.686 deg. </A> <br>
- <A HREF="./cf_09.742.ellipsys"> Skin Friction Distribution - Angle of Attack = 09.742 deg. </A> <br>
- <A HREF="./cf_11.712.ellipsys"> Skin Friction Distribution - Angle of Attack = 11.712 deg. </A> <br>
- <A HREF="./cf_14.000.ellipsys"> Skin Friction Distribution - Angle of Attack = 14.000 deg. </A> <br>
- <A HREF="./cf_15.190.ellipsys"> Skin Friction Distribution - Angle of Attack = 15.190 deg. </A> <br>
- <A HREF="./cf_16.000.ellipsys"> Skin Friction Distribution - Angle of Attack = 16.000 deg. </A>


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<H1>FIGURES AVAILABLE: (PostScript files)</H1><p><p>

- <A HREF="./PS/profile.ps"> Airfoil shape </A><p>

- <A HREF="./PS/cl.ps"> Lift Coefficient </A><br>
- <A HREF="./PS/cd.ps"> Drag Coefficient </A><br>
- <A HREF="./PS/cm.ps"> Moment Coefficient </A><p>

- <A HREF="./PS/cp_a07.686.ps"> Pressure Distribution - Angle of Attack = 07.686 deg. </A><br>
- <A HREF="./PS/cp_a09.742.ps"> Pressure Distribution - Angle of Attack = 09.742 deg. </A><br>
- <A HREF="./PS/cp_a11.712.ps"> Pressure Distribution - Angle of Attack = 11.712 deg. </A><br>
- <A HREF="./PS/cp_a14.000.ps"> Pressure Distribution - Angle of Attack = 14.000 deg. </A><br>
- <A HREF="./PS/cp_a15.190.ps"> Pressure Distribution - Angle of Attack = 15.190 deg. </A><br>
- <A HREF="./PS/cp_a16.000.ps"> Pressure Distribution - Angle of Attack = 16.000 deg. </A><p>

- <A HREF="./PS/cf_a07.686.ps"> Skin Friction Distribution - Angle of Attack = 07.686 deg. </A><br>
- <A HREF="./PS/cf_a09.742.ps"> Skin Friction Distribution - Angle of Attack = 09.742 deg. </A><br>
- <A HREF="./PS/cf_a11.712.ps"> Skin Friction Distribution - Angle of Attack = 11.712 deg. </A><br>
- <A HREF="./PS/cf_a14.000.ps"> Skin Friction Distribution - Angle of Attack = 14.000 deg. </A><br>
- <A HREF="./PS/cf_a15.190.ps"> Skin Friction Distribution - Angle of Attack = 15.190 deg. </A><br>
- <A HREF="./PS/cf_a16.000.ps"> Skin Friction Distribution - Angle of Attack = 16.000 deg. </A><p>



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